EASA AD No.: 2014-0080

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0080

Date: 27 March 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption]. 

### Design Approval Holder’s Name:
AIRBUS HELICOPTERS Type/Model designation(s): AS 332 L2 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: None



### ATA 67 Rotor Flight Controls – Yaw Control Damper Support – Inspection / Replacement

Manufacturer(s): Airbus Helicopters (formerly Euroc opter, Eurocopter France, Aerospatiale)
Applicability: AS 332 L2 helicopters, all serial nu mbers, equipped with yaw control damper support Part Number (P/N) P/N 332A25-1334-00.

Reason: Several cases of cracks of the two front at tachment points of the yaw control damper support were reported. The subsequent invest igations determined that pilot actions on the yaw pedals could generate detr imental loading conditions on the support attachment points and initiate crack s. This condition, if not detected and corrected, coul d lead to structural failure of the yaw control damper support, resulting in detach ment of the damper unit, possibly blocking of the yaw flight control channel and consequent reduced control of the helicopter. To address this potential unsafe condition, Airbus Helicopters issued Alert Service Bulletin (ASB) No. AS332-05.00.98 to provid e inspection and replacement instructions. For the reasons described above, this AD requires r epetitive inspections of the yaw control damper support and, depending on findin gs, replacement.

Effective Date: 03 April 2014EASA AD No.: 2014-0080

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within the compliance time as specified in Tabl e 1 of this AD, and, thereafter, at intervals not to exceed 825 flight h ours (FH), inspect the four attachment points of the yaw control damper support in accordance with the instructions of Airbus Helicopters ASB No. AS33 2-05.00.98.
Table 1 Compliance time

FH accumulated on the effective date of this AD Compliance Time
Less than 3 900 FH Before exceeding 4 000 FH
Equal to or more than 3 900 FH Within 100 FH after the effective date of this AD (2) If, during any inspection as required by paragr aph (1) of this AD, any crack on the yaw control damper support is detected, befo re next flight, replace the affected support with a serviceable part in acc ordance with the instructions of Airbus Helicopters ASB No. AS332-05 .00.98. (3) Replacement of a yaw control damper support on a helicopter, as required by paragraph (2) of this AD, does not constitute te rminating action for the repetitive inspections as required by paragraph (1) of this AD for that helicopter.
Ref. Publications: Airbus Helicopters ASB No. AS332 -05.00.98 original issue, dated 26 March 2014. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Airbus Helicopters – Aéroport de Marseille Provence 13725 Marignane Cedex, France Telephone +33 (4) 42 85 97 97, Facsimile +33 (4) 42 85 99 66 E-mail: Directive.technical-support@eurocopter.com

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